Aeroplane



Dec. 15, 1931.

R; E. w|KE AEROPLANE Filed June 10 1929 3 Sheets-Sheet 1 ATTORNEYS Dec. 15, 1931] WIK 1,836,351

AEROPLANE Filed June 10, 1929 3 Sheets-Sheet 2 INVENTOR R. E. WlKE AEROPLANE Dec. 15, 1931.

Filed June '10, 1929 3 Sheets-Sheet liilllll l illll llllll lll INVENTOR 'zra/c/ ATTORNEYS Patented acr 15, 1931 Application filed June to,

' This invention relates to aeroplanes and has particular reference to an aeroplane provided with means for efi'ecting both vertical and horizontal flights.

One of the primary objects of this invention is to provide an aeroplane with wings mounted for rotation in a horizontal plane to exert a lifting force on the aeroplanetogether with means for adjusting the angle of incidence of these wings.

A further object of this invention is to provide an aeroplane having win of the above mentioned character toget er with means for automatically balancing the angles of incidence of said wings to thus eliminate the danger of said wings exerting an upsetting force on the aeroplane.

The invention further contemplates the provision of a plurality of propellers for ef- 2 fecting a forward drive of the aeroplane together with a'novel means for mounting a motor for driving the said propellers and the first mentioned wings, whereby the wind resistance will be decreased to a minimum.

Other objects and advantages of the invention together with the numerous novel details of construc-tipn will become more apparent as the following description proceeds, particularly when reference is had to the accompa'ny'ing drawings wherein Figure 1 is a semi-diagrammatic elevationalview partly in section of an aeroplane showing the invention applied to the same;

Figure 2 is a detail perspective view of a portion of the aeroplane shown in Figure 1;

Figure 3 is a vertical sectional view taken substantially on the line 3+3 of Figure 1;

Figure 4 is an elevational view partly in section of a portion of the aeroplane shown in' Figure 1,'showin-g the actuating mechanism for the propellers,;

Figures 5 to 7 inclusive are-sectional views taken substantially on the lines-5%), 6-6

and 7- 7 of Figure 2; and I Fi re 8 is a view similar to Figure 2, showing a slightly modified form of .construction.

Referring now particularly to the drawings wherein like reference characters designate corresponding parts throughout all 1929. Serial No. 368,798.

views, there is-semi-diagrammatically illustrated in Figure 1 an aeroplane includin the fuselage 10, this fuselage being provide in accordance with the usual practice'with the rudders 11 and landing gear 12.

Fixed to the fuselage 10 and adjacent the forward end of the same, as by the brackets 15, is a motor 16, this motor being preferably of the radial type and being horizontally mounted as clearly illustrated in Figure 1 of 39 the drawings. The horizontal mountin of the motor permits the formation of the uselage with a stream line forward end, thus decreasing to a considerable extent the wind resistahceto the travel of the aeroplane. The

horizontal mounting of the motor 16 posse'sses a further advantage since b virtue of this mounting,-the motor is in t e rear of and in alignment with the propellers adjacent the centers of the latter. Since the pitch of the-propeller blades increases toward'the centers of the propellers, more ail. will be forced rearwardlyand into contact with the motor to cool the same by virtue of its arrangement adjacent the centers of the propellers. Thus, regardless of the pitch of the propeller blades air will always be forced rearwardly into contact with the motor during rotation of the propeller.

The motor'16'is provided with a shaft 17 89 and fixed to the end of this shaftis a bevel gear 18 adapted for driving engagement with the gears 19 and20 respectively. Ifdesiredan idler gear 21 may be mounted for engagement with the gears 19 and 20 at a point opposite the gear 18 to aid in maintaining the ears 19* and 20in position. The gear 21 is s own as mounted on'a shaft 22 and while this shaft may, as illustrated, be a stub shaft having its ends journaled in a bearing 23, it is to be clearly understood that if desired this shaft may be extended for connection to a second radial motor horizontally arranged above the gears19 and 20. The gear 18 may. bear any desired relation to the gears 19 and 20 and in practice it has been found desirable to make the relation substantially 1 to 2, whereby the gears 19 and 20 are driven half as fast as the gear 18.

' The bevel gear 20 is connected by a one-way 'l a be eccentric to the axis ofthe shaft ,as will be clearly apparent by reference .to the above drive clutch, designated generally by the reference character 30, to a bevel gear 31 whereby the gear 31 may be driven from the gear 20 but may rotate faster than this gear. The

' gear 31 is arranged in meshing engagement with the gears 32 and '33, it being understood that by this arrangement these gears will be rotated in counter-directions. If desired a suitable idler gear 34 may be provided for meshing engagement with the opposite sides of the gears 32 and 33 to aid in maintaining these gears in their proper positions.

The gears 32 and 33 are adapted to drive the wings 35 and 36 respectively, these wings being mounted for rotation in horizontal planes above the fuselage 10 as clearly illustrated in Figure 1 of the drawings. For accomplishing this, the gear 33 is fixed to a sleeve 40 which projects vertically above the fuselage a predetermined desired distance. As shown in Figure 2 of the drawings, there is fixed to the upper end of the sleeve 40 a collar 41 provided with the diametrically 0pposed sockets 42. Each socket forms a mounting for a shaft 43 and mounted on each shaft 43 is a blade 44. The blades 44 may be pivotally mounted on the shafts 43 as illustrated or the blades may be fixed to the shafts, the shafts in this case being journaled in the sockets. The blades 44 are oppositely mounted whereby the lifts on these blades are on opposite sides of the shafts 43, as clearly illustrated in Figure'2 of the drawin s. The two blades 44 form the wing 36 and t is wing is adapted to be rotated as a unit bythe sleeve 40 in the direction of the arrows in Figure 2 of the drawings.

For driving the wing 35 there is provided a shaft 45 fixed to the gear 32 and extending upwardly through the sleeve 40. This shaft is provided at its free end-with the collar 46 formed with the diametrically opposed hubs 47 for receiving the shafts 48. Blades 49 are pivotally .mounted on these shafts, these blades being mounted in a manner similar to the blades 44, whereby the lift on one blade is on oneside of its shaft while the lift on the other blade is on the opposite side of its shaft. The blades 49 form the wing 35 and this wing will be rotated in a direction counter to the direction of rotation of the wing 36 as clearly illustrated by the arrows in Figure 2 of the drawings.

The blades 44 and 49'are preferably of the cross sectional shape shown in Figures 5 to 7 inclusive, it being. noted that the blades taper. gradually from their inner to their outer ends. Throughout its length however, each blade is so mounted on its respective shaft, that the center of lift on the blade will mentioned figures. It will be further noted thatin mounting the blades on their respective shafts,each shaft is offset from the upper surface of its respective blade, whereby the lage. The lever is provided with a handle end 58 whereb the same may be. actuated and if desired there may be provided a guide member 59 provided with the notches 60 in which the lever is adapted to be engaged for indicating the angle of adjustment of the lever 55 and for holding the lever in adjusted position.

The opposite end of the lever is bifurcated and is pivotally fixed to the vertically extending rods 60, these rods lying on opposite sides of the sleeve 40 as clearly illustrated in Figure 2 of the drawings. The rods 60 are pivotally connected at their upper ends to a ring 61 rotatably mounted on a sleeve 62. The sleeve 62 is mounted for sliding movement on the sleeve 40 and may rotate with this sleeve relative to the rods 60 by virtue of the rotatable mounting of the ring 61.

Pivotally mounted on the sleeve 62 and adjacent the upper end-of the same is a yoke 65 provided with the diametrically extending arms 66; Pivoted to the outer end of the arms 66 are the links 67 which project vertically betweenthe blades 44 of the wings 36. At its end each link 67 pivotally engages a pin 68 fixed as at 69 to one of the blades 44. It will be noted that the pins 68 engage the blades 44 on the unbalanced sides of the blades, whereby vertical movement of the sleeve" 62 on the sleeve 40 will effect a vertical movement of the rods 67 and will thus vary the angles of incidence of the blades 44. Thus with the angle of incidence of the blades 44 at zero, in which position the wing 36 will have but a slight lifting effect, the sleeve 62 may be moved vertically and this vertical movement will be transmitted to the unbalanced sides of the blades 44 to elevate the entering edges of these blades to thus increase the angle of incidence of the blades and to increase the elevating effect of the wing 36. It

will be obvious that-theblades 44 will be side of one of the Wings just the 7 9; The sleeve 79 is slidably mounted on the shaft and pivoted to this sleeve is a yoke 80 having the diametrically opposed arms 81 to the outer ends of which are secured links 82 connected at their opposite ends to pins 83, each pinbeing fixed to the unbalanced 49. Thus it will be seen that vertical movement of the sleeve 62 will be transmitted to the sleeve 7 9 and will in turn be transmitted to the links 82 through the yoke 80 and arms 81 to adjust the angle of incidence of the blades 49.

lhus the lever may be adjusted to vary the angle of incidence oi the wings 35 and 36 at the will of the operator and to thus adjust the elevating e'fiect of these wings. It will be clearly apparent that by virtue of the arrangement of links connecting the lever 55 to the blades 44 and 49, these blades will be simultaneously adjusted uponadjustment of the lever. Further, it the blades of the wings are all initially set at the same angle of incidence, adjustment of the lever 55 will effect a substantially equal adjustment of all of the angles of incidence of all of the blades. In practice, however, it may be desirable to adblades of wing 35- to one angle and the blades of wing 36 to a different angle and to accomplish this, separate adjusting mechanisms may be provided. To accomplish this result without providing separate adjusting mechanisms, the blades 49 of the wing 35 may be initially set ata'n blades 44 of the wing 36, in which event during the adjustment of spective wings, the angles of incidence of the blades 49-'will always bear a predetermined relation to the angles of incidence oi the blades 44. Thus for example the blades 7 49 may, if desired, be set at zero degrees while whereby upon adjustment of the the blades 44 may be set at minus two degrees, blades by the lever 55, the blades 49 will always'be'at an angle of incidence two degrees greater than the angle of incidence of the blades 44.

The arrangement above described, in addition to providing means for adjusting the angle of incidence on the blades, functions further to effect an automatic balancing of the blades of each wing. Considering first the wing 35 which includes the blades 49 and assuming that during the rotation of this wing an upward force is exerted 'on the unbalanced side of one ofthe blades, this upward force will tend to move this blade about its pivot 48 and this movement will be trans- 'mitted through the pin 83 fixed to the blade and the link 82, to he yoke which will to thus draw rock about its pivot point 80':

. the link connebted to the other blade downwardly. Thus as theforce acting upwardly on the one blade-tends to decrease the angle of incidence of this blade,'th'elinks connecting this blade to the other blade of the same angle difiering from the the blades of the re-' at the same angle of with the wings wing will tend to increase the angle of incidence on'the second mentioned blade, so that the sum total of the angles of incidence on both blades of each wing will always be the same. For example, if the angles of incidence are set to 15 and a force is exerted on the one blade of the wing tending to increase the angle of incidence of this blade to 20, the links connecting this blade to the other blade will function to immediately decrease the angle of. incidence of the other blade of the same wing to approximately 10, so that the total of the two angles of incidence will be 30 or the same as originally adjusted.

Thisautomatic balancing efiect eliminates all danger of the aeroplane being upset by gustsof wind acting on the blades of the wings 35 and 36, it being clearly understood that the blades 44 will be balanced relative to each other in the manner described in connection with the blades 49. Thus with the blades adjusted to the desiredangle of incidence, which adjustment may be made manually through the lever 55, the sum total of the angles of incidence of all of the blades will be the same by virtue of the automatic balancing efiect of the connecting links. It will be understood that if one blade of one wing is upset sli htly so that the angle of incidence of one% angle of incidence of the other blade is in lade is decreased and the a equalize the angles of incidence so that during normal operation, the pivoted yokes will be substantially horizontal, the blades being incidence.

The invention further provides a pair of propellers for efiecting a forward movement of the aeroplane. Thus as illustrated, in Figure 1 of the drawings, there is provided a propeller and a second propeller 91. The propeller-9O is connected by a shaft 92 to the gear 20 while the propeller 91 is connected by a sleeve 93 to the gear 19. Thus the propellers will be rotated in opposite direct-ions in the same manner as are the wings 35 and 36.

In order that the pitch of the propeller blades may be adjusted at the will of the operator, an arrangement similar to the arrangement of levers described in connection 35 and 36 is provided. In detail the adjusting mechanism includes a lever arm 95 mounted adjacent the lever arm 55 for movement longitudinally of the fuselage. The forward end of this lever is bifurcated and is connected to a sleeve 96 mounted for longitudinal movement on the sleeve 93.

Rotatable on the sleeve 96 is a ring 97 and pivoted to this ring are the links 98 pivotally connected at their ends to the blades 99 of the propeller 91. The links 98 are also pivotally connected to the links 100 which in turn are pivotally connected to a ring 101 blades 104 .sliding movement of the sleeve rotatably mounted on a sleeve 102 slidably mounted on the shaft 92. Pivotally connected to the sleeve 102 are the links 103 which in turn are connected at their ends to the blades 104 of the propellor 90.

It will be seen that longitudinal movement of the lever 95 will effect a movement of the sleeve 96 longitudinally of the sleeve 93. This movement will be transmitted to the propeller the pitch of these blades and will further be transmitted to the sleeve 102 by the links 100. Longitudinal movement of the sleeve 102 on the shaft 92 will be transmitted to the of the propeller 90 by the links 103 to thus adjust the pitch of the blades 104.

In Figure 8 a slightly modified form of construction is shown to take the place of the construction shown in Figure 2 of' the drawings. In the modified construction the links 70 and the yoke 76 are eliminated, the I 62 being transmitted directly to the sleeve 79.

Thus as illustrated, the sleeve 62 may be slidably mounted on the sleeve 40 and may be adapted for actuation by the links in the same manner as is the sleeve 62. Pivoted to the sleeve 62 is a yoke 65 connected by the links 67 to the blades 44. Slidably mounted on-the shaft 45 is a sleeve 7 9 and pivoted to this sleeve is a yoke 80 connected by the links 82 to the wings 49. Instead however, of transmitting movement of the sleeve 69 to the sleeve 79 by virtue of links 70 and yoke 75, rods 110 may be provided, these rods being fixed to the sleeve 62 as at 111 and being fixed as at 112 to a ring 113 rotatably mounted on the sleeve 79. Thus, vertical movement of the sleeve 62 will be transmitted directly to the sleeve 7 9 irrespective of the operation of the links which adjustthe blades 44.

From the above it is believed that the structure and operation of the invention will be clearly apparent. The wings 35 and 36 in addition to providing means for e'flecting a vertical flight of the plane, take the place of the wings normally mount d on an aeroplane. These wings are adapted to be driven in opposite directions by the motor 16 and are connected to the motor 16 by the one-way or overrunning clutch 30 whereby they may not only rotate faster than the motor but may also be movedrelative to each other independently of the motor for alignment with the fuselage of the aeroplane. While the clutch 30 is shown as being mounted between the gear 20 and the gear 31, it will be clearly apparent that this clutch may, if desired,

be eliminated at this point and similar clutches may be provided between the sleeve 40 and wing 36 and the shaft 45 and wing 35. Thus the wings 35. and 36 may be moved into alignment with the fuselage, permitting housing of the aeroplane in a hangar.

blades 99 by the links 98 to vary-- In flying the plane the motor may be started to drive the wings 35 and 36, it being understood that these wings rotate in opposite directions in the manner described. The angles of incidence of the blades 44 and 49 may be adjusted to cause the wings 35 and 36 to exert an upward pull on the aeroplane as will be clearly apparent. The propellers 90 and 91 will be rotated with the wings 35 and 36 and when the desired elevation is reached the propellers 90 and 91 may be adjusted to cause the same to exert a forward ull on the aeroplane. During flying of the p ane the pitch of the propellers 90 and 91 together with the angles of incidence of the blades 44 and 49 may be varied at will to correspondingly regulate the upward and forward travel of the plane. When it is desired to descend the angles of incidence of the blades 44 and 49 may be properly adjusted to permit a gliding of the plane to its landing. Obviously if the motor should die during flight of the plane, the wings 35 and 36 may be adjusted as above mentioned to permit gliding of the plane to its landing.

I With the plane in flight and the blades 44 and 49 properly adjusted to give the desired lift to the aeroplane, any force exerted on one of the blades of either of the wings tending to upset the plane Will be immediately compensated for by the balancing means above-described. Thus, if the angle of incidence of one blade of one wing is independently increased by an upsetting force, the angle of incidence of the other blade of the same wing will be correspondingly decreased so that the total angles of incidence of the two blades of each wing will remain the same.

The actuating mechanism for adjusting the blades of the wings 35 and 36 may extend on the outside of the sleeve 40 as illustrated or may be arranged centrally of the shaft 45 as will be clearly apparent. Further the reduction gearing between the motor 16 and the wings 35 and 36 and propellers 90 and 91 will permit the propellers and the wings to rotate more slowly than the motor, thus giving more power at a lower speed. Since there are two propellers and two wings, the propellers and wings need only rotate at one half the speed of the motor if such an arrangement is desired.

While the invention has been described with considerable detail it will be understood that the description is for the purposes of illustration only and is not definitive of the limits of the inventive idea. The right is therefore reserved to make such changes in the details of construction and arrangement of parts as will fall within the purview of the attached claims.

What I claim as my invention is:

1. In an aeroplane, a fuselage, a pair of horizontally aligned blades mounted for ro- I tal shaft for pivotal lage, and means for simultaneously adjusting the angles of incidence of said blades to the same degree, said means being operable upon movement of one of said blades out of the adjusted angle of incidence to simultaneously move the other blade to oppositely adjust the angle of incidence thereof.

2. In an aeroplane, a fuselage, a pair of horizontally aligned blades mounted for rotation in a horizontal plane above said fuselage, and means for adjusting the angles of incidence of said blades, said means being operable upon the independent increase of the angle of incidence of one ofsaid blades to correspondingly decrease cidence of the other blade.

3. In. an aeroplane, a fuselage, a shaft projecting vertically from said fuselage, a pair of horizontally arranged shafts having the angle of inaligned axes fixed to said vertical shaft, a

blade eccentrically mounted on each horlzontal shaft'for pivotal movement thereon, and means for equally adjusting the angles of incidence of said blades and operable upon an independent change in the angle of incidence of one of said blades to oppositely adjust the angle of incidence of the other blade.

' 4. .In an aeroplane, a fuselage, a shaft projecting vertically from said fuselage, a pair of horizontally arranged shafts having aligned axes fixed to said vertical shaft, a

blade eccentrically mounted on each horizonmovement thereon, and means for equally adjusting the angles of incidence of said blades and operable upon an independent change in the angle of incidence of one of. said adjust the angle of incidence of the other -blade, said last mentioned means including alink connected to the unbalanced side of Y eachblade, and a pivotally mounted yoke connecting said links.

5. In an aeroplane, a fuselage, -a shaft projecting vertically from said fuselage, a pair of horizontally arranged aligned axes fixed to said vertical shaft, a blade eccentriclly mounted on each horizontal shaft for pivotal movement thereon, and means for equally adjusting the angles of incidence of said blades and operable upon an independent change in the angle of incidence of one of said blades to oppositely adjust the angle of incidence of the other blade, said last mentioned means including a link connected to the unbalanced side of each blade, a yoke pivotally and slidably mounted on-said vertical shaft connecting said links, and means for moving said yoke'longitudinally of said vertical shaft.

6. In an aeroplane, a pair ,of wings -of all of said blades,

. wing,

blades to oppositely shafts having ing operable to adjustthe blades of each g to the same angle of incidence and to oppositel adjust the angle of incidence of each bla e the angle of incidence of the other blade ofthe same wingf 7. In an aeroplane, a pair of wings mounted for rotation in opposite directions, each wing including a pair of blades, a single means for adjusting the angles of incidence said means being operable to adjust the'blades of each wing to the same angle of incidence and to oppositely adjust the angle of incidence of each blade upon an independent change in the angle of.

other blade of the same incidence of the a motor for rotating said wings, and a one-Way clutch between said motor and said wings permitting rotation of said wings relative to said motor while permitting driving of said wings by said motor.

8'. In anaeroplane, a. fuselage, a pair of axially aligned blades mounted for'rotation relative to said fuselage, and means for equally adjusting the angles of incidence 0 said blades, said means being operable upon an independent change in the angle of incidence of one of said blades to oppositely adjust the angle of incidence of the other blade.

9. In an aeroplane, a fuselage, a shaft carried by said fuselage, a pair of shafts having aligned axes fixed to said first mentioned shaft, a blade eccentrically mounted on each of said second mentioned shafts for pivotal movement thereof, and means for equally adjusting the angles of incidence of said blades and for balancing the angles of incidence thereof, said means including a link connected to the unbalanced side of each blade, a sleeve slidably mounted on said first mentioned shaft, a yoke pivotally mounted 'on saidsleeve and connected to said links, and means for moving said sleeve longitudinally of said first mentioned shaft.

In testimony whereof I aflix my signature.

REGINALD E. WIKE.

-- -mounted,fo r rotation in opposite directions,

each wing including a pair of'blades, and a single means for adjusting the angles of incidence of all of said-blades,

said means be upon an independent change m' Ill 

